US3894324A - Rotor for fluid flow machines - Google Patents

Rotor for fluid flow machines Download PDF

Info

Publication number
US3894324A
US3894324A US280142A US28014272A US3894324A US 3894324 A US3894324 A US 3894324A US 280142 A US280142 A US 280142A US 28014272 A US28014272 A US 28014272A US 3894324 A US3894324 A US 3894324A
Authority
US
United States
Prior art keywords
rotor
ring member
inner ring
outer ring
disk
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US280142A
Other languages
English (en)
Inventor
Immanuel Holzapfel
Gerhard Zahring
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Application granted granted Critical
Publication of US3894324A publication Critical patent/US3894324A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making

Definitions

  • ABSTRACT A rotor arrangement and method of making the rotor arrangement for fluid flow machines having a plurality of rotor disks, each including a plurality of rotor blades, spaced from one another by intermediate ring members.
  • the intermediate ring members are constructed as inner and outer rings with the inner ring welded to the adjacent rotor disk and the outer ring detachably slidably engaged over the inner ring by a dove-tail connection.
  • the outer surface of the outer rings form a continuous surface with rotor blade platforms. Locking elements are connected at the platforms and the disk to hold the blades and outer rings from axial movement.
  • a modification dispenses with the outer ring and includes labyrinth points on the inner ring which sealingly cooperates with a ring member of stator vane cascades interposed between the disks.
  • the present invention relates to a rotor for fluid flow machines in which a plurality of rotor disks are interconnected by means of intermediate rings welded or otherwise fixed in place between them.
  • Rotors in this category can normally not be disassembled, so that it is very nearly impossible to replace damaged components in especially the outer circumferential area of the rotor, such as the rotor blades attached to the rotor or to the rotor disks.
  • a broad object of the present invention is to eliminate the disadvantages attributed to said rotors for fluid flow machines and to provide a rotor which permits of relatively high operating speeds and possesses the requisite strength to sustain such speeds while overcoming the abovediscussed disadvantages and while having a comparatively low dead weight.
  • the present invention contemplates the provision of a rotor for fluid flow machines of the said generic category in which the intermediate rings each include an inner member which is welded in place and an outer member which is slipped into place on the inner member. It is further contemplated by the present invention that said outer member forms a smoothly faired inner wall for the as sociated flow duct in conjunction with the platforms on adjacent blades.
  • the inner members of the intermediate rings may be permanently connected to the disks by electron beam or friction welding.
  • the inner members of the intermediate rings may further be composed of individual segments.
  • the present invention contemplates the provision of the outer member as a continuous closed ring and the provision of corresponding detachably slidably interengageable parts for circumferentially, and radially locking an inner and outer member together.
  • the present invention contemplates the provision of similar configurations for the interengageable parts on a plurality of axially aligned inner members so as to facilitate free passage of an outer member in the axial direction of the rotor over and past several inner members to a position in engagement with the corresponding mating inner member.
  • Preferably enough play is provided for permitting passage of the outer member without leaving excess slack that cannot be taken up by elasticity of the outer member when finally assembled and used.
  • each intermediate ring forms a continuous ring having radially disposed internal teeth for sliding it axially into mating slots in the inner member of the intermediate ring, where the respective shape and number, or pitch, of these slots are essentially identical with the shape and pitch of the slots in the remaining inner members but will still ensure free passage of the outer member when this is being slipped into place.
  • the teeth could be provided on the inner member and the slots on the outer members.
  • each intermediate ring is prevented from excessively expanding radially under service loads.
  • a comparatively large number of suitably selected dovetailed teeth and slots ensures a maximally central position of the outer member of each intermediate ring.
  • dovetail slots in the inner members of the intermediate rings and in the outer members of the intermediate rings may be produced by broaching much like the dovetail slots in the blade shrouds of rotor disks.
  • the dovetail slots in the inner members of the intermediate rings may be broached before welding exactly like those in the rotor disks.
  • the accuracy obtainable in shape and pitch of the dovetail slots in the outer and inner member of each intermediate ring contemplated by the present invention may be in the order of magnitude of that of the dovetail slots in rotor disks.
  • the outer member of each intermediate ring may be made elastic within reasonable limits, minor deviations in the shape of the outer member of the intermediate rings can be readily compensated during assembly.
  • the present invention contemplates that the dovetail contour can be repeated unchanged on the same radius through several rotor stages, so that a corresponding number of outer members of the intermediate rings can he slipped with their teeth through the slots in the inner members of the intermediate rings.
  • the present invention eontcmplates that the interengageable parts of several rotor stages be similar for inclined contour ducts.
  • the blades and with them also the outer members of the intermediate rings may be arrested in their axial position by means of locking elements.
  • a further modification contemplated by the present invention is the arrangement of the inner members of the intermediate rings to be reworked to provide, for instance, labyrinth points, and that rotors intended for use in compressors may thus be retrofitted for cooperation with internally shrouded vane cascades.
  • the present invention further contemplates the method of making the rotor arrangements referred to above.
  • FIG. I is a longitudinal center section view of a rotor in accordance with the present invention which schematically illustrates the step-by-step assembly of the retor;
  • FIG. 2 is a schematic longitudinal center section view of the fully assembled rotor of FIG. 1;
  • FIG. 3 is a partial schematic sectional view, with portions cut-away, taken along line IIII of FIG. 2;
  • FIG. 4 is a detail schematic view illustrating the configuration and attachment of the blade root to one of the rotor disks of FIGS. 1 and 2', and
  • FIG. 5 is a longitudinal center section schematic view illustrating an alternative embodiment of the rotor shown in FIGS. I and 2.
  • the numeral 2 indicates an axial-flow compressor rotor which essentially comprises of the rotor disks 3, 4, 5, and 6. These rotor disks 3, 4, 5, and 6 are interconnected by welding them in the areas of their shrouds 7, 8, 9, and I to the inner members I1, 12, I3, of the intermediate rings 14, I and 16.
  • the welded axial-flow compressor rotor is fitted alternately and viewed from left to right with the rotor blades 18, I9, 20, 2] and the outer members 22, 23, 24, of the intermediate rings 14, l5, 16 (FIG. 1) preferably to suit the cross-sectional area of the compressor air duct 17 (FIG. 2) which may be narrowing in the direction of flow.
  • the outer member 24, which forms a continuous ring, of the intermediate ring 16 is then slipped over the mating inner member 13 until its face contacts with the airfoil platform 27 of the blade 21.
  • a dovetailed connection 28 arrests the outer member 24 in its circumferential as well as radial position on the inner member 13 of the intermediate ring 16.
  • the pitch and the contour of the teeth and of their mating slots in the dovetail connection 28 are approximately identical with those in the dovetail connections 29, 30 (FIG. 2) of the intermediate rings 15, I4, so that the continuous-ring member 24 may readily be slipped with its teeth through the slots in the inner members ll, 12 of the intermediate rings I4, entering in the dovetail connections 29, 30.
  • the attachment or assembly of the remaining outer members 22, 23 and blades 20, I9, I8 then proceeds analogously, where the outer members 22, 23 of the intermediate rings 15, 14 form, together with the platforms 3], 32, 33, of the blades 18, I9, a smoothly faired inner wall for the air duct 17 (FIG. 2).
  • FIG. 3 exemplifies a representative dovetailed connection 29 between the welded inner member 12 and the subsequently axially seated outer member 23 of the intermediate ring 15.
  • FIG. 2 shows additional locking plates 34, 35, 36 which limit the blade to disk connections at the forward end and are arranged between the respective shrouds 7, 8, 9 (FIG. I) and blade platforms 31, 32, 33.
  • FIG. 2 further illustrates the outer duct wall 27 of the compressor air duct 17 which contains stator vanes 38, 39, 40.
  • FIGS. I and 2 exemplify an axial-flow compressor rotor 2 where the stator vane cascades are unshrouded at their inner diameter so that when the rotor is turning, the fixedly arranged outer members 22, 23, 24 of the intermediate rings 14, l5, 16 are completely free to move below the free ends of the stator vanes 38, 39, 40 without the intervention of sealing devices.
  • FIG. 5 illustrates an axial-flow compressor rotor 41 which differs from the embodiment on FIGS. 1 and 2 in that the inner member 12 of the intermediate ring 15 which was formerly slotted to accommodate the dovetailed connection 29 has now been shaped by reworking (42 in FIG. 5) to provide labyrinth points 43 which together with the inner ring 45 attached to the stator vanes 44, form a non-contacting or a contacting seal.
  • the rotor disks are indicated with the numerals 46, 47 and their rotor blades with 48, 49.
  • FIGS. 1 to 5 may analogously be applied also to a turbine rotor.
  • each of the inner and outer members could include both teeth and slots engageable with corresponding teeth and slots on the other member.
  • other interengageable connections than dovetail connections could be used.
  • a method of making a rotor arrangement comprising:
  • said plurality of rotor disks includes at least three rotor disks. further comprising: slidably inserting a plurality of rotor blades in slots provided at the periphery of a second disk adjacent the endmost disk,
  • a method according to claim 32, wherein said steps of fixedly attaching said inner ring members to said disks includes welding of the respective inner ring members to respective ones of said disks.
  • a method of making a rotor arrangement comprising:

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US280142A 1971-08-14 1972-08-14 Rotor for fluid flow machines Expired - Lifetime US3894324A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2140816A DE2140816A1 (de) 1971-08-14 1971-08-14 Rotor fuer stroemungsmaschinen

Publications (1)

Publication Number Publication Date
US3894324A true US3894324A (en) 1975-07-15

Family

ID=5816766

Family Applications (1)

Application Number Title Priority Date Filing Date
US280142A Expired - Lifetime US3894324A (en) 1971-08-14 1972-08-14 Rotor for fluid flow machines

Country Status (4)

Country Link
US (1) US3894324A (enrdf_load_stackoverflow)
DE (1) DE2140816A1 (enrdf_load_stackoverflow)
FR (1) FR2150094A5 (enrdf_load_stackoverflow)
GB (1) GB1395957A (enrdf_load_stackoverflow)

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3986793A (en) * 1974-10-29 1976-10-19 Westinghouse Electric Corporation Turbine rotating blade
US4050134A (en) * 1974-10-29 1977-09-27 Westinghouse Electric Corporation Method for removing rotatable blades without removing the casting of a turbine
US4127359A (en) * 1976-05-11 1978-11-28 Motoren-Und Turbinen-Union Munchen Gmbh Turbomachine rotor having a sealing ring
US4277225A (en) * 1977-09-23 1981-07-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor for jet engines
US4310286A (en) * 1979-05-17 1982-01-12 United Technologies Corporation Rotor assembly having a multistage disk
US4483054A (en) * 1982-11-12 1984-11-20 United Technologies Corporation Method for making a drum rotor
US4645424A (en) * 1984-07-23 1987-02-24 United Technologies Corporation Rotating seal for gas turbine engine
US4743165A (en) * 1986-10-22 1988-05-10 United Technologies Corporation Drum rotors for gas turbine engines
US4767272A (en) * 1987-10-14 1988-08-30 United Technologies Corporation Method for reducing blade tip variation of a bladed rotor
US5660526A (en) * 1995-06-05 1997-08-26 Allison Engine Company, Inc. Gas turbine rotor with remote support rings
US6406263B1 (en) 1999-04-13 2002-06-18 Honeywell International, Inc. Gas turbine shaft pilot system with separate pilot rings
US20040202544A1 (en) * 2003-04-08 2004-10-14 Henning Thomas Richard Methods and apparatus for assembling rotatable machines
US20050180847A1 (en) * 2004-02-14 2005-08-18 Alstom Technology Ltd Rotor
US20060153684A1 (en) * 2005-01-10 2006-07-13 Henning Thomas R Methods and apparatus for assembling rotatable machines
CN103025480A (zh) * 2010-08-06 2013-04-03 斯奈克玛 制造涡轮发动机鼓的方法
US20130108466A1 (en) * 2011-10-28 2013-05-02 Gabriel L. Suciu Asymetrically slotted rotor for a gas turbine engine
US20130108468A1 (en) * 2011-10-28 2013-05-02 Gabriel L. Suciu Spoked spacer for a gas turbine engine
US20130108445A1 (en) * 2011-10-28 2013-05-02 Gabriel L. Suciu Spoked rotor for a gas turbine engine
US8757980B2 (en) 2010-04-01 2014-06-24 Snecma Rotor for a gas turbine engine comprising a rotor spool and a rotor ring
US20160186591A1 (en) * 2014-12-31 2016-06-30 General Electric Company Flowpath boundary and rotor assemblies in gas turbines

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2293628B (en) * 1994-09-27 1998-04-01 Europ Gas Turbines Ltd Turbines

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2497151A (en) * 1946-03-04 1950-02-14 Armstrong Siddeley Motors Ltd Multidisk rotor
US2548886A (en) * 1947-10-25 1951-04-17 Gen Electric Gas turbine power plant with axial flow compressor
US2662685A (en) * 1949-07-13 1953-12-15 Materiels Hispano Suiza S A So Rotor for fluid machines
US2743080A (en) * 1949-04-29 1956-04-24 Ruston & Hornsby Ltd Turbine rotors
US2749086A (en) * 1951-08-23 1956-06-05 Rolls Royce Rotor constructions for turbo machines
US2840299A (en) * 1952-09-22 1958-06-24 Thompson Prod Inc Axial flow compressor rotor
US2928649A (en) * 1954-09-28 1960-03-15 Rolls Royce Rotors of turbines and compressors
US2998959A (en) * 1955-09-29 1961-09-05 Rolls Royce Bladed rotor of axial-flow fluid machine with means to retain blades in position on rotor
US3094309A (en) * 1959-12-16 1963-06-18 Gen Electric Engine rotor design
US3295825A (en) * 1965-03-10 1967-01-03 Gen Motors Corp Multi-stage turbine rotor

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2497151A (en) * 1946-03-04 1950-02-14 Armstrong Siddeley Motors Ltd Multidisk rotor
US2548886A (en) * 1947-10-25 1951-04-17 Gen Electric Gas turbine power plant with axial flow compressor
US2743080A (en) * 1949-04-29 1956-04-24 Ruston & Hornsby Ltd Turbine rotors
US2662685A (en) * 1949-07-13 1953-12-15 Materiels Hispano Suiza S A So Rotor for fluid machines
US2749086A (en) * 1951-08-23 1956-06-05 Rolls Royce Rotor constructions for turbo machines
US2840299A (en) * 1952-09-22 1958-06-24 Thompson Prod Inc Axial flow compressor rotor
US2928649A (en) * 1954-09-28 1960-03-15 Rolls Royce Rotors of turbines and compressors
US2998959A (en) * 1955-09-29 1961-09-05 Rolls Royce Bladed rotor of axial-flow fluid machine with means to retain blades in position on rotor
US3094309A (en) * 1959-12-16 1963-06-18 Gen Electric Engine rotor design
US3295825A (en) * 1965-03-10 1967-01-03 Gen Motors Corp Multi-stage turbine rotor

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3986793A (en) * 1974-10-29 1976-10-19 Westinghouse Electric Corporation Turbine rotating blade
US4050134A (en) * 1974-10-29 1977-09-27 Westinghouse Electric Corporation Method for removing rotatable blades without removing the casting of a turbine
US4127359A (en) * 1976-05-11 1978-11-28 Motoren-Und Turbinen-Union Munchen Gmbh Turbomachine rotor having a sealing ring
US4277225A (en) * 1977-09-23 1981-07-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor for jet engines
US4310286A (en) * 1979-05-17 1982-01-12 United Technologies Corporation Rotor assembly having a multistage disk
US4483054A (en) * 1982-11-12 1984-11-20 United Technologies Corporation Method for making a drum rotor
US4645424A (en) * 1984-07-23 1987-02-24 United Technologies Corporation Rotating seal for gas turbine engine
US4743165A (en) * 1986-10-22 1988-05-10 United Technologies Corporation Drum rotors for gas turbine engines
US4767272A (en) * 1987-10-14 1988-08-30 United Technologies Corporation Method for reducing blade tip variation of a bladed rotor
US5660526A (en) * 1995-06-05 1997-08-26 Allison Engine Company, Inc. Gas turbine rotor with remote support rings
US6406263B1 (en) 1999-04-13 2002-06-18 Honeywell International, Inc. Gas turbine shaft pilot system with separate pilot rings
US20040202544A1 (en) * 2003-04-08 2004-10-14 Henning Thomas Richard Methods and apparatus for assembling rotatable machines
US6908285B2 (en) * 2003-04-08 2005-06-21 General Electric Company Methods and apparatus for assembling rotatable machines
US20050180847A1 (en) * 2004-02-14 2005-08-18 Alstom Technology Ltd Rotor
US7476078B2 (en) * 2004-02-14 2009-01-13 Alstom Technology Ltd Rotor with core surrounded by shielding rings
US20060269403A9 (en) * 2004-02-14 2006-11-30 Alstom Technology Ltd Rotor
US7287958B2 (en) 2005-01-10 2007-10-30 General Electric Company Methods and apparatus for assembling rotatable machines
US20060153684A1 (en) * 2005-01-10 2006-07-13 Henning Thomas R Methods and apparatus for assembling rotatable machines
US8757980B2 (en) 2010-04-01 2014-06-24 Snecma Rotor for a gas turbine engine comprising a rotor spool and a rotor ring
CN103025480A (zh) * 2010-08-06 2013-04-03 斯奈克玛 制造涡轮发动机鼓的方法
US9073155B2 (en) 2010-08-06 2015-07-07 Snecma Method of fabricating a turbine engine drum
US8944762B2 (en) * 2011-10-28 2015-02-03 United Technologies Corporation Spoked spacer for a gas turbine engine
US20130108445A1 (en) * 2011-10-28 2013-05-02 Gabriel L. Suciu Spoked rotor for a gas turbine engine
US8784062B2 (en) * 2011-10-28 2014-07-22 United Technologies Corporation Asymmetrically slotted rotor for a gas turbine engine
US20140294589A1 (en) * 2011-10-28 2014-10-02 United Technologies Corporation Asymmetrically slotted rotor for a gas turbine engine
US20130108468A1 (en) * 2011-10-28 2013-05-02 Gabriel L. Suciu Spoked spacer for a gas turbine engine
US20130108466A1 (en) * 2011-10-28 2013-05-02 Gabriel L. Suciu Asymetrically slotted rotor for a gas turbine engine
US9790792B2 (en) * 2011-10-28 2017-10-17 United Technologies Corporation Asymmetrically slotted rotor for a gas turbine engine
US9938831B2 (en) * 2011-10-28 2018-04-10 United Technologies Corporation Spoked rotor for a gas turbine engine
US20180223668A1 (en) * 2011-10-28 2018-08-09 United Technologies Corporation Spoked rotor for a gas turbine engine
US10760423B2 (en) * 2011-10-28 2020-09-01 Raytheon Technologies Corporation Spoked rotor for a gas turbine engine
US20160186591A1 (en) * 2014-12-31 2016-06-30 General Electric Company Flowpath boundary and rotor assemblies in gas turbines
US9664058B2 (en) * 2014-12-31 2017-05-30 General Electric Company Flowpath boundary and rotor assemblies in gas turbines

Also Published As

Publication number Publication date
DE2140816A1 (de) 1973-03-01
GB1395957A (en) 1975-05-29
FR2150094A5 (enrdf_load_stackoverflow) 1973-03-30

Similar Documents

Publication Publication Date Title
US3894324A (en) Rotor for fluid flow machines
US3867060A (en) Shroud assembly
US4907944A (en) Turbomachinery blade mounting arrangement
US3182955A (en) Construction of turbomachinery blade elements
US5302086A (en) Apparatus for retaining rotor blades
US3761200A (en) Bladed rotors
US4011718A (en) Gas turbine construction
US5584654A (en) Gas turbine engine fan stator
US3814539A (en) Rotor sealing arrangement for an axial flow fluid turbine
US3997280A (en) Stators of axial turbomachines
US4743166A (en) Blade root seal
US3689177A (en) Blade constraining structure
US2640679A (en) Turbine or compressor stator ring
US2766963A (en) Turbine stator assembly
US4015910A (en) Bolted paired vanes for turbine
EP0343361A1 (en) Turbine vane shroud sealing system
US3841792A (en) Turbomachine blade lock and seal device
JPH0233844B2 (enrdf_load_stackoverflow)
GB1461965A (en) Axial flow turbine structure
US3656864A (en) Turbomachine rotor
US3702222A (en) Rotor blade structure
GB2089900A (en) Locking of rotor blades on a rotor disk
US7828521B2 (en) Turbine module for a gas-turbine engine
US3248081A (en) Axial locating means for airfoils
US2857132A (en) Turbine wheel